US8579581B2 - Abradable bucket shroud - Google Patents

Abradable bucket shroud Download PDF

Info

Publication number
US8579581B2
US8579581B2 US12/882,311 US88231110A US8579581B2 US 8579581 B2 US8579581 B2 US 8579581B2 US 88231110 A US88231110 A US 88231110A US 8579581 B2 US8579581 B2 US 8579581B2
Authority
US
United States
Prior art keywords
curve
abradable
ridges
shroud
bucket
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active, expires
Application number
US12/882,311
Other languages
English (en)
Other versions
US20120063881A1 (en
Inventor
James Albert Tallman
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
GE Infrastructure Technology LLC
Original Assignee
General Electric Co
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by General Electric Co filed Critical General Electric Co
Assigned to GENERAL ELECTRIC COMPANY reassignment GENERAL ELECTRIC COMPANY ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: TALLMAN, JAMES ALBERT
Priority to US12/882,311 priority Critical patent/US8579581B2/en
Priority to DE102011053048.7A priority patent/DE102011053048B4/de
Priority to CH01494/11A priority patent/CH703758B1/de
Priority to JP2011197910A priority patent/JP5802493B2/ja
Priority to CN201110283399.5A priority patent/CN102434220B/zh
Publication of US20120063881A1 publication Critical patent/US20120063881A1/en
Publication of US8579581B2 publication Critical patent/US8579581B2/en
Application granted granted Critical
Assigned to GE INFRASTRUCTURE TECHNOLOGY LLC reassignment GE INFRASTRUCTURE TECHNOLOGY LLC ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: GENERAL ELECTRIC COMPANY
Active legal-status Critical Current
Adjusted expiration legal-status Critical

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material

Definitions

  • the present application relates generally to gas turbine engines and more particularly relates to an optimal shape for an abradable pattern on a bucket shroud for use in a gas turbine engine and the like.
  • Abradable coatings have been applied to the surface of the turbine shroud to help establish a minimum or optimum clearance between the shroud and the bucket tips, i.e., the bucket tip gap. Such a material may be readily abraded by the tips of the buckets with little or no damage thereto. As such, bucket tip gap clearances may be reduced with the assurance that the abradable coating will be sacrificed instead of the bucket tip material.
  • an abradable surface as a pattern of ridges and the like thereon has been found to provide additional aerodynamic benefits in further reducing the leakage flow therethrough.
  • the ridges may provide direction to the mainstream flow away from the tip clearance gap.
  • Known abradable patterns thus have been found to provide aerodynamic benefits in the reduction of the minimum tip clearance height and otherwise.
  • Such an abradable bucket shroud pattern may be optimized for a specific bucket design in terms of the leakage flow therethrough and the heat loads thereon. Specifically, such a bucket shroud design would provide an adequate abradable shroud surface in the context of a flow reducing pattern for improved performance.
  • the present application thus provides an abradable bucket shroud for use with a bucket tip so as to limit a leakage flow therethrough and reduce heat loads thereon.
  • the abradable bucket shroud may include a base and a number of ridges positioned thereon.
  • the ridges may be made from an abradable material.
  • the ridges may form a pattern.
  • the ridges may have a number of curves with at least a first curve and a second curve and with the second curve having a reverse camber shape.
  • the present application further provides a method of minimizing a leakage flow through a bucket tip gap between a bucket tip and a shroud.
  • the method may include the steps of determining a direction of the leakage flow across the bucket tip gap at a number of reference points along the bucket tip, positioning a number of abradable material ridges on the shroud, and forming the abradable material ridges into at least a first curve and second curve.
  • the first curve may have a blockage position normal to the leakage flow at the reference points.
  • the present application further provides an abradable bucket shroud for use with a bucket tip so as to limit a leakage flow therethrough and reduce heat loads thereon.
  • the abradable bucket shroud may include a base and a number of parallel ridges positioned therein.
  • the ridges may be made from an abradable material.
  • the ridges may include a pattern with a sinusoidal shape having at least a first curve and a second curve. The first curve may have a normal position to the leakage flow therethrough.
  • FIG. 1 is a schematic view of a gas turbine engine.
  • FIG. 2 is a side plan view of a known bucket and shroud of a portion of a turbine stage.
  • FIG. 3 is a side plan view of an abradable shroud as may be described herein positioned adjacent to a bucket tip.
  • FIG. 4 is a plan view of an abradable pattern on the shroud as may be described herein with an outline of the outer surface of a turbine bucket tip shown in phantom lines across the pattern ridges.
  • FIG. 5 is a schematic view of a bucket tip with leakage flows shown thereon.
  • FIG. 1 shows a schematic view of a gas turbine engine 10 as may be described herein.
  • the gas turbine engine 10 may include a compressor 15 .
  • the compressor 15 compresses an incoming flow of air 20 .
  • the compressor 15 delivers the compressed flow of air 20 to a combustor 25 .
  • the combustor 25 mixes the compressed flow of air 20 with a compressed flow of fuel 30 and ignites the mixture to create a flow of combustion gases 35 .
  • the gas turbine engine 10 may include any number of combustors 25 .
  • the flow of combustion gases 35 is in turn delivered to a turbine 40 .
  • the flow of combustion gases 35 drives the turbine 40 so as to produce mechanical work.
  • the mechanical work produced in the turbine 40 drives the compressor 15 and an external load 45 such as an electrical generator and the like.
  • the gas turbine engine 10 may use natural gas, various types of syngas, and/or other types of fuels.
  • the gas turbine engine 10 may be one of any number of different gas turbine engines offered by General Electric Company of Schenectady, N.Y. such as a heavy duty 7FA gas turbine engine and the like.
  • the gas turbine engine 10 may have other configurations and may use other types of components.
  • Other types of gas turbine engines also may be used herein.
  • Multiple gas turbine engines 10 , other types of turbines, and other types of power generation equipment also may be used herein together.
  • FIG. 2 shows an example of a portion of a turbine stage 50 .
  • Each turbine stage 50 includes a rotating turbine blade or bucket 55 .
  • each turbine bucket 55 may include a shank 60 , a platform 65 , an extended airfoil 70 , and a bucket tip 75 .
  • the bucket tip 75 may have one or more cutting teeth 80 thereon.
  • Other configurations and other types of buckets 55 may be used herein.
  • Each rotating bucket 55 may be positioned adjacent to a stationary shroud 85 .
  • the shroud 85 may have a number of seals 90 thereon that cooperate with the bucket tip 85 of each bucket 55 .
  • the shroud 85 may include a number of abradable ridges as will be described in more detail below.
  • Other configurations and other types of shrouds 85 and seals 90 may be used herein.
  • the airfoil 70 diverts the energy of the expanding flow of combustion gases 35 into mechanical energy.
  • the bucket tip 75 may provide a surface that runs substantially perpendicular to the surface of the airfoil 70 .
  • the bucket tip 75 thus also may help to hold the flow of combustion gases 35 on the airfoil 70 such that a greater percentage of the flow of combustion gases 35 may be converted into mechanical energy.
  • the stationary shroud 85 increases overall efficiency by directing the flow of combustion gases 35 onto the airfoil 70 as opposed to through a bucket tip gap 95 between the bucket tip 75 and the shroud 85 . Minimizing the bucket tip gap 95 thus helps to minimize a leakage flow therethrough as is described above. Other configurations also may be used herein.
  • FIG. 3 shows an abradable shroud 100 as may be described herein.
  • the abradable shroud 100 may include a number of ridges 110 positioned on a base surface 120 .
  • the ridges 110 may be made out of an abradable material 130 .
  • the abradable material generally may be made out of a metallic and/or a ceramic alloy. Any type of abradable material may be used herein.
  • the abradable material 130 also may be positioned on the base surface 120 and elsewhere.
  • the ridges 110 of the abradable shroud 100 may form an abradable pattern 140 thereon.
  • a contact patch 150 with the outline of the bucket tip 75 is shown in phantom lines.
  • An arrow 160 shows the direction of rotation of the turbine bucket 55 with respect to the abradable pattern 140 .
  • An arrow 170 indicates the direction of the flow of combustion gases 35 with respect to the abradable pattern 140 .
  • the ridges 110 may be substantially parallel to each other and also may be substantially equidistant. The spacing and the shape of the ridges 110 , however, may vary with position.
  • the ridges 110 may have any desired depth and/or cross-sectional shape. Other configurations may be used herein.
  • the ridges 110 may have a substantially sinusoidal shape 180 with at least a concave or a first curve 190 followed by a convex or a second curve 200 extending from a forward portion 220 to an aft portion 230 .
  • the abradable pattern 140 thus has a double arc shape with the second curve having a reverse camber 210 shape as compared to the first curve 190 .
  • Other types of patterns may be used herein.
  • Other types and numbers of curves may be used herein.
  • the abradable pattern 140 may be optimized with respect to the shape of the associated bucket tip 75 .
  • the relative positioning of the abradable shroud 100 and the bucket 55 is shown in FIG. 3 with the bucket tip gap 95 positioned therebetween.
  • the abradable shroud 100 is stationary while the bucket 55 is rotating.
  • the relative motion between the bucket tip 75 and the abradable shroud 100 may give rise to a timed periodic pressure pulsation 145 acting on a leakage flow 240 extending therethrough due to the passing of the pattern 140 of the ridges 110 .
  • This unsteady pressure may lead to a net reduction of the leakage flow 240 through the tip gap 95 as compared to an axially symmetric shroud with the same or a similar gap 95 therethrough.
  • the ridges 110 of the abradable shroud 110 combine to limit the leakage flow 240 therethrough.
  • FIG. 5 illustrates the leakage flow 240 through the bucket tip gap 95 .
  • the leakage velocity vectors are shown in a frame of reference relative to the bucket tip 75 .
  • the direction of the leakage flow 240 at a mid-cord reference point 245 is illustrated with an arrow 250 at about twenty degrees (20°) from the axis of rotation.
  • the leakage flow 240 is seen at an arrow 260 at an angle of about fifty-five degrees (55°).
  • a stationary ridge 110 oriented at about negative thirty-five degrees ( ⁇ 35°) thus will be at a normal or a blockage position 265 to the leakage flow path 95 .
  • Such a blockage position 265 thus may provide the maximum blockage angle as the ridge 110 moves relative to the tip gap 95 .
  • This process then may be repeated at several reference points 245 along the length of the bucket tip 75 to create the shape of at least the first curve 190 of the pattern 140 .
  • Many different patterns 140 thus may be formed based upon this process based upon the type of bucket, the type of turbine, specific operating conditions, and other variables.
  • the angle of the leakage flow 240 varies with the axial position within the tip gap 95 .
  • the optimum blocking angle also may vary along the length of the bucket tip 75 .
  • the sinusoidal shape 180 of FIG. 4 thus maximizes the optimum blocking angle given the shape of the specific bucket tip 75 along the length thereof.
  • the abradable pattern 140 thus has the concave or the first curve 190 on the forward portion 220 thereof and the convex or the second curve 200 of the reverse camber 210 on the aft portion 230 . Again, many different patterns 140 thus may be formed herein.
  • all of the ridges 110 increase heat transfer because they have more wetted surface area.
  • the pattern 140 may be optimized such that the first curve 190 about the forward portion 320 provides improved blocking while the second curve 200 or the reverse camber 210 about the aft portion 230 prevents overheating.
  • the ridges 110 also may establish an optimum recirculation flow 270 between adjacent ridges 110 . This inter ridge recirculation flow 270 may be made up of cool air that may be retained between adjacent buckets 55 .
  • the pattern 140 thus balances leakage reduction with reduced heat transfer.
  • the abradable shroud 100 with the abradable pattern 140 thus limits the leakage flow 240 therethrough and the issues associated therewith such as aerodynamic performance degradation and increased shroud heat loads.
  • the abradable pattern 140 may be optimized with respect to the leakage flow 240 passing over the bucket tip 75 and the overall heat transfer.
  • Other types of abradable patterns 140 may be used with other types and shapes of bucket tips.
  • the abradable shroud 100 described herein is noticeably cooler and provides less leakage flow 240 therethrough about the forward portion 320 thereof.
  • the aft portion 230 may be somewhat warmer, but less warm than it would otherwise be with similar leakage flows therethrough.
  • the reduction in the leakage flow 240 thus reduces the aerodynamic losses about the bucket 55 and the shroud 100 so as to provide higher efficiency. Likewise, the thermal load on the shroud 100 may be reduced so as to improve overall durability and component lifetime.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US12/882,311 2010-09-15 2010-09-15 Abradable bucket shroud Active 2032-03-02 US8579581B2 (en)

Priority Applications (5)

Application Number Priority Date Filing Date Title
US12/882,311 US8579581B2 (en) 2010-09-15 2010-09-15 Abradable bucket shroud
DE102011053048.7A DE102011053048B4 (de) 2010-09-15 2011-08-26 Abtragbare Laufschaufelummantelung und Verfahren zum Minimieren einer Leckströmung durch einen Laufschaufelspitzenspalt
CH01494/11A CH703758B1 (de) 2010-09-15 2011-09-09 Laufschaufelummantelung mit Rippen aus einem abtragbaren Material.
JP2011197910A JP5802493B2 (ja) 2010-09-15 2011-09-12 摩耗性バケットシュラウド
CN201110283399.5A CN102434220B (zh) 2010-09-15 2011-09-15 可磨损动叶围带

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US12/882,311 US8579581B2 (en) 2010-09-15 2010-09-15 Abradable bucket shroud

Publications (2)

Publication Number Publication Date
US20120063881A1 US20120063881A1 (en) 2012-03-15
US8579581B2 true US8579581B2 (en) 2013-11-12

Family

ID=45756218

Family Applications (1)

Application Number Title Priority Date Filing Date
US12/882,311 Active 2032-03-02 US8579581B2 (en) 2010-09-15 2010-09-15 Abradable bucket shroud

Country Status (5)

Country Link
US (1) US8579581B2 (de)
JP (1) JP5802493B2 (de)
CN (1) CN102434220B (de)
CH (1) CH703758B1 (de)
DE (1) DE102011053048B4 (de)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20170051626A1 (en) * 2014-02-25 2017-02-23 Siemens Aktiengesellschaft Turbine abradable layer with composite non-inflected bi-angle ridges and grooves
US10612407B2 (en) 2013-02-28 2020-04-07 United Technologies Corporation Contoured blade outer air seal for a gas turbine engine

Families Citing this family (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9598969B2 (en) 2012-07-20 2017-03-21 Kabushiki Kaisha Toshiba Turbine, manufacturing method thereof, and power generating system
JP5951387B2 (ja) * 2012-07-20 2016-07-13 株式会社東芝 ラビリンスシール部およびタービン
CN103883361B (zh) * 2012-12-20 2016-05-04 中航商用航空发动机有限责任公司 涡轮叶片
US9816392B2 (en) * 2013-04-10 2017-11-14 General Electric Company Architectures for high temperature TBCs with ultra low thermal conductivity and abradability and method of making
CN103422912B (zh) * 2013-08-29 2015-04-08 哈尔滨工程大学 一种包括叶顶带有孔窝的动叶片的涡轮
US8939716B1 (en) 2014-02-25 2015-01-27 Siemens Aktiengesellschaft Turbine abradable layer with nested loop groove pattern
US9249680B2 (en) 2014-02-25 2016-02-02 Siemens Energy, Inc. Turbine abradable layer with asymmetric ridges or grooves
US9243511B2 (en) 2014-02-25 2016-01-26 Siemens Aktiengesellschaft Turbine abradable layer with zig zag groove pattern
US8939706B1 (en) * 2014-02-25 2015-01-27 Siemens Energy, Inc. Turbine abradable layer with progressive wear zone having a frangible or pixelated nib surface
US9151175B2 (en) 2014-02-25 2015-10-06 Siemens Aktiengesellschaft Turbine abradable layer with progressive wear zone multi level ridge arrays
EP3111051A1 (de) * 2014-02-25 2017-01-04 Siemens Aktiengesellschaft Turbinenringsegment mit abreibbarer schicht mit zusammengesetztem winkel, asymmetrischem oberflächendichtefirst und rillenmuster
US8939705B1 (en) 2014-02-25 2015-01-27 Siemens Energy, Inc. Turbine abradable layer with progressive wear zone multi depth grooves
RU2016137904A (ru) 2014-02-25 2018-03-29 Сименс Акциенгезелльшафт Термобарьерное покрытие компонента турбины с изолирующими трещины техническими элементами в виде канавок
JP2017521552A (ja) * 2014-05-15 2017-08-03 ヌオーヴォ ピニォーネ ソチエタ レスポンサビリタ リミタータＮｕｏｖｏ Ｐｉｇｎｏｎｅ Ｓ．Ｒ．Ｌ． ターボマシンの構成要素を製造する方法、ターボマシンの構成要素、および、ターボマシン
WO2016133583A1 (en) 2015-02-18 2016-08-25 Siemens Aktiengesellschaft Turbine shroud with abradable layer having ridges with holes
EP3259452A2 (de) 2015-02-18 2017-12-27 Siemens Aktiengesellschaft Formung von kühlpassagen in verbrennungsturbine-superlegierungsgussteilen
CN112031878A (zh) * 2020-11-05 2020-12-04 中国航发沈阳黎明航空发动机有限责任公司 一种涡轮转子叶片叶尖双层壁结构

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20030175116A1 (en) * 2001-11-14 2003-09-18 Snecma Moteurs Abradable coating for gas turbine walls
US6660405B2 (en) 2001-05-24 2003-12-09 General Electric Co. High temperature abradable coating for turbine shrouds without bucket tipping
US20050003172A1 (en) * 2002-12-17 2005-01-06 General Electric Company 7FAstage 1 abradable coatings and method for making same
US6887528B2 (en) 2002-12-17 2005-05-03 General Electric Company High temperature abradable coatings
US6916529B2 (en) 2003-01-09 2005-07-12 General Electric Company High temperature, oxidation-resistant abradable coatings containing microballoons and method for applying same
US20060110248A1 (en) * 2004-11-24 2006-05-25 Nelson Warren A Pattern for the surface of a turbine shroud
US7500824B2 (en) 2006-08-22 2009-03-10 General Electric Company Angel wing abradable seal and sealing method
US7600968B2 (en) 2004-11-24 2009-10-13 General Electric Company Pattern for the surface of a turbine shroud

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3019920C2 (de) * 1980-05-24 1982-12-30 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Einrichtung zur äußeren Ummantelung der Laufschaufeln von Axialturbinen für Gasturbinentriebwerke
JPH10266804A (ja) * 1997-03-26 1998-10-06 Mitsubishi Heavy Ind Ltd チップシュラウド翼キャビティ
EP1591626A1 (de) * 2004-04-30 2005-11-02 Alstom Technology Ltd Schaufel für Gasturbine
EP1715140A1 (de) * 2005-04-21 2006-10-25 Siemens Aktiengesellschaft Turbinenschaufel mit einer Deckplatte und einer auf der Deckplatte aufgebrachte Schutzschicht
US8622784B2 (en) 2008-07-02 2014-01-07 Huffman Corporation Method for selectively removing portions of an abradable coating using a water jet

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6660405B2 (en) 2001-05-24 2003-12-09 General Electric Co. High temperature abradable coating for turbine shrouds without bucket tipping
US20030175116A1 (en) * 2001-11-14 2003-09-18 Snecma Moteurs Abradable coating for gas turbine walls
US20050003172A1 (en) * 2002-12-17 2005-01-06 General Electric Company 7FAstage 1 abradable coatings and method for making same
US6887528B2 (en) 2002-12-17 2005-05-03 General Electric Company High temperature abradable coatings
US6916529B2 (en) 2003-01-09 2005-07-12 General Electric Company High temperature, oxidation-resistant abradable coatings containing microballoons and method for applying same
US20060110248A1 (en) * 2004-11-24 2006-05-25 Nelson Warren A Pattern for the surface of a turbine shroud
US7600968B2 (en) 2004-11-24 2009-10-13 General Electric Company Pattern for the surface of a turbine shroud
US7614847B2 (en) 2004-11-24 2009-11-10 General Electric Company Pattern for the surface of a turbine shroud
US7500824B2 (en) 2006-08-22 2009-03-10 General Electric Company Angel wing abradable seal and sealing method

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10612407B2 (en) 2013-02-28 2020-04-07 United Technologies Corporation Contoured blade outer air seal for a gas turbine engine
US20170051626A1 (en) * 2014-02-25 2017-02-23 Siemens Aktiengesellschaft Turbine abradable layer with composite non-inflected bi-angle ridges and grooves
US9631506B2 (en) * 2014-02-25 2017-04-25 Siemens Aktiengesellschaft Turbine abradable layer with composite non-inflected bi-angle ridges and grooves

Also Published As

Publication number Publication date
DE102011053048B4 (de) 2022-07-21
CN102434220B (zh) 2015-08-26
CH703758B1 (de) 2016-02-15
CN102434220A (zh) 2012-05-02
CH703758A2 (de) 2012-03-15
DE102011053048A1 (de) 2012-03-15
JP5802493B2 (ja) 2015-10-28
JP2012062887A (ja) 2012-03-29
US20120063881A1 (en) 2012-03-15

Similar Documents

Publication Publication Date Title
US8579581B2 (en) Abradable bucket shroud
US7614847B2 (en) Pattern for the surface of a turbine shroud
US8075256B2 (en) Ingestion resistant seal assembly
US7600968B2 (en) Pattern for the surface of a turbine shroud
US8419356B2 (en) Turbine seal assembly
US9476317B2 (en) Forward step honeycomb seal for turbine shroud
US9822659B2 (en) Gas turbine with honeycomb seal
JP2010019261A (ja) タービンダブテール用のスプリングシール
US9810074B2 (en) Segmented turbine blade squealer tip and cooling method
EP3841281A1 (de) Verbesserte zweitstufenturbinenschaufel
US10472980B2 (en) Gas turbine seals
US20150147169A1 (en) Adjusted stationary airfoil
WO2017119898A1 (en) Turbine blade with multi-layer multi-height blade squealer
EP2412934A2 (de) Mantelringsegment einer Turbinenstufe
US20130236293A1 (en) Systems and methods for an improved stator
US20190136700A1 (en) Ceramic matrix composite tip shroud assembly for gas turbines
US9528380B2 (en) Turbine bucket and method for cooling a turbine bucket of a gas turbine engine
JP5400500B2 (ja) タービンダブテール用のラビリンスシール
CN110662884B (zh) 具有凹槽尖端和致密的氧化物弥散强化层的涡轮机叶片
JP2011080465A (ja) 半径方向シールピン
WO1996015356A1 (en) An improved airfoil structure
US10247013B2 (en) Interior cooling configurations in turbine rotor blades
US10301967B2 (en) Incident tolerant turbine vane gap flow discouragement
WO2019177599A1 (en) Canted honeycomb abradable structure for a gas turbine

Legal Events

Date Code Title Description
AS Assignment

Owner name: GENERAL ELECTRIC COMPANY, NEW YORK

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:TALLMAN, JAMES ALBERT;REEL/FRAME:024988/0642

Effective date: 20100914

FEPP Fee payment procedure

Free format text: PAYOR NUMBER ASSIGNED (ORIGINAL EVENT CODE: ASPN); ENTITY STATUS OF PATENT OWNER: LARGE ENTITY

STCF Information on status: patent grant

Free format text: PATENTED CASE

CC Certificate of correction
FPAY Fee payment

Year of fee payment: 4

MAFP Maintenance fee payment

Free format text: PAYMENT OF MAINTENANCE FEE, 8TH YEAR, LARGE ENTITY (ORIGINAL EVENT CODE: M1552); ENTITY STATUS OF PATENT OWNER: LARGE ENTITY

Year of fee payment: 8

AS Assignment

Owner name: GE INFRASTRUCTURE TECHNOLOGY LLC, SOUTH CAROLINA

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:GENERAL ELECTRIC COMPANY;REEL/FRAME:065727/0001

Effective date: 20231110